Abstract
The aerodynamics of hypersonic vehicles is highly affected by enthalpy or “real gas” effects. The purpose of the current study is to assess the proper formulation of computational fluid dynamics required for simulation of high-enthalpy flows. Under the assumption of chemical and thermal equilibrium, a functional representation has been employed for specific heat at constant pressure, thermal conductivity, and viscosity coefficients for air at 500 to 30,000 K and pressure range of 10−4 to 100 atm. The proposed approach is evaluated using double-cone configuration at hypersonic flow. It is shown that the equivalent gas model is capable of capturing the main features of these flow fields and compares well with experiments.
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Shitrit, S., Arad, E. (2019). Hypersonic Flow Computations by Using an Equivalent Gas Model. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_111
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DOI: https://doi.org/10.1007/978-3-319-91017-8_111
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